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FR3115822B1 - MODULARITY OF AN AIRCRAFT TURBOMACHINE - Google Patents

MODULARITY OF AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3115822B1
FR3115822B1 FR2011339A FR2011339A FR3115822B1 FR 3115822 B1 FR3115822 B1 FR 3115822B1 FR 2011339 A FR2011339 A FR 2011339A FR 2011339 A FR2011339 A FR 2011339A FR 3115822 B1 FR3115822 B1 FR 3115822B1
Authority
FR
France
Prior art keywords
module
reducer
turbomachine
splines
compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2011339A
Other languages
French (fr)
Other versions
FR3115822A1 (en
Inventor
Paul Ghislain Albert Levisse
Olivier Belmonte
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2011339A priority Critical patent/FR3115822B1/en
Priority to EP21811415.5A priority patent/EP4240951B1/en
Priority to PCT/FR2021/051914 priority patent/WO2022096814A1/en
Priority to CN202180080437.9A priority patent/CN116568908A/en
Priority to US18/251,278 priority patent/US11933230B2/en
Publication of FR3115822A1 publication Critical patent/FR3115822A1/en
Application granted granted Critical
Publication of FR3115822B1 publication Critical patent/FR3115822B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/026—Shaft to shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Retarders (AREA)
  • General Details Of Gearings (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Turbomachine (10) d’aéronef, cette turbomachine ayant un axe longitudinal (A) et comportant : - un corps haute pression appelé HP, - un corps basse pression appelé BP, - une soufflante (48), et - un réducteur (36) à train épicycloïdal, caractérisé en ce que le corps BP comprend trois modules : - un premier module (22) comportant la turbine BP (24) et l’arbre BP (26), , - un second module (28) comportant le compresseur BP (30) et un tourillon (68) solidaire du rotor du compresseur BP, et - un troisième module (32) comportant un arbre d’entrée (34) du réducteur (36), cet arbre d’entrée comportant une extrémité amont d’accouplement à un solaire (38) du réducteur et une extrémité aval comportant des premières cannelures (74) qui sont orientées parallèlement audit axe et qui sont configurées pour être engagées dans des secondes cannelures (76) complémentaires dudit second module (28). Figure pour l'abrégé : Figure 1Aircraft turbomachine (10), this turbomachine having a longitudinal axis (A) and comprising: - a high pressure body called HP, - a low pressure body called LP, - a fan (48), and - a reducer (36) with planetary gear train, characterized in that the LP body comprises three modules: - a first module (22) comprising the LP turbine (24) and the LP shaft (26), - a second module (28) comprising the LP compressor (30) and a trunnion (68) integral with the rotor of the LP compressor, and - a third module (32) comprising an input shaft (34) of the reducer (36), this input shaft comprising an upstream end of coupling to a sun gear (38) of the reducer and a downstream end comprising first splines (74) which are oriented parallel to said axis and which are configured to be engaged in second splines (76) complementary to said second module (28). Figure for abstract: Figure 1

FR2011339A 2020-11-04 2020-11-04 MODULARITY OF AN AIRCRAFT TURBOMACHINE Active FR3115822B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2011339A FR3115822B1 (en) 2020-11-04 2020-11-04 MODULARITY OF AN AIRCRAFT TURBOMACHINE
EP21811415.5A EP4240951B1 (en) 2020-11-04 2021-11-02 Modularity of an aircraft turbomachine
PCT/FR2021/051914 WO2022096814A1 (en) 2020-11-04 2021-11-02 Modularity of an aircraft turbomachine
CN202180080437.9A CN116568908A (en) 2020-11-04 2021-11-02 Modularization of aircraft turbines
US18/251,278 US11933230B2 (en) 2020-11-04 2021-11-02 Modularity of an aircraft turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011339 2020-11-04
FR2011339A FR3115822B1 (en) 2020-11-04 2020-11-04 MODULARITY OF AN AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3115822A1 FR3115822A1 (en) 2022-05-06
FR3115822B1 true FR3115822B1 (en) 2022-09-30

Family

ID=74125463

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011339A Active FR3115822B1 (en) 2020-11-04 2020-11-04 MODULARITY OF AN AIRCRAFT TURBOMACHINE

Country Status (5)

Country Link
US (1) US11933230B2 (en)
EP (1) EP4240951B1 (en)
CN (1) CN116568908A (en)
FR (1) FR3115822B1 (en)
WO (1) WO2022096814A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3130877B1 (en) * 2021-12-20 2024-10-25 Safran Aircraft Engines FLUID TRANSFER DEVICE WITH HYDRAULIC AND MECHANICAL CONNECTION MEANS
FR3140123A1 (en) 2022-09-26 2024-03-29 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE BY AN AXIAL AND ROTATIONAL LOCKING DEVICE, CORRESPONDING ASSEMBLY METHOD
US12247518B2 (en) * 2023-04-28 2025-03-11 Pratt & Whitney Canada Corp. Retainer and method for disassembling an aircraft engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1110245A (en) * 1966-10-14 1968-04-18 Rolls Royce Coupling
US3631688A (en) * 1970-10-19 1972-01-04 Gen Motors Corp Shaft coupling locking device and tool for installation thereof
US3958887A (en) * 1973-11-13 1976-05-25 Rolls-Royce (1971) Limited Shaft couplings
US5433674A (en) * 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
FR2940247B1 (en) * 2008-12-19 2011-01-21 Snecma SYSTEM OF CONTRAROTATIVE PROPELLERS DRAWN BY AN EPICYCLOIDAL TRAIN PROVIDING A BALANCED TORQUE DISTRIBUTION BETWEEN THE TWO PROPELLERS
FR2975149B1 (en) * 2011-05-09 2013-06-07 Snecma SYSTEM FOR ATTACHING TWO TUBULAR PIECES, ONE IN ANOTHER BEARING A BEARING BEARING
FR3013388B1 (en) * 2013-11-21 2019-03-22 Safran Aircraft Engines ENGINE, SUCH AS A TURBOJET, MODULAR WITH SPEED REDUCER
FR3075874B1 (en) * 2017-12-22 2019-11-22 Safran Aircraft Engines REDUCING TURBOMACHINE FOR AN AIRCRAFT
US20190345876A1 (en) * 2018-05-11 2019-11-14 Rolls-Royce Deutschland Ltd & Co Kg Method of positioning two parts relative to each other in a formlocking connection, a formlocking device and gas turbine engine

Also Published As

Publication number Publication date
EP4240951B1 (en) 2025-01-01
EP4240951A1 (en) 2023-09-13
US11933230B2 (en) 2024-03-19
US20230417192A1 (en) 2023-12-28
WO2022096814A1 (en) 2022-05-12
FR3115822A1 (en) 2022-05-06
CN116568908A (en) 2023-08-08

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